Deceleration discriminating firing device for a fuze



Aug. 6, 1957 H. c. FILBERT, JR 2,801,588

DECELERATION DISCRIMINATING FIRING DEVICE FOR A FUZE Filed Aug. 31,1949 3 Sheets-Sheet 1 I 42 '77 As H w, WWW:

Aug. 6, 1957 c FlLBERT, JR 2,801,588

DECELERATION DISCRIMINATING FIRING DEVICE FOR A FUZE Filed Aug. 31, 1949 3 Sheets-Sheet 2 n lllll i mm mm 1957 H. c. FILBERT, JR 88 DECELERATION DISCRIMINATING FIRING DEVICE FOR A FUZE Filed Aug. 31. 1949 3 Sheets-Sheet 3 H a FILBERT, .11:

3% wr y United States Patent ()7 DECELERATION DISCRIMINATING FiRIN G DEVICE FOR A F UZE Howard C. Filbert, Jr., Baltimore, Md.

Application August 31, 1949, Serial No. 113,442

15 Claims. (Cl. 10270.2)

(Granted under Title 35, U. S. Code (1952), sec. 266) This invention relates generally to a fuze for use in an armor piercing rocket, projectile or the like and more particularly to a deceleration discriminating firing mechanism therefor.

More especially the invention relates to a firing device for a fuze in which means are provided for firing an electroresponsive detonator disposed within the fuze thereby to initiate explosion of the missile when the deceleration of the missile has decreased toward zero value, such, for example, as when the missile has penetrated the outer plates of a naval vessel, aircraft or the like and decelerates within the interior thereof, or upon partial penetration of heavy armor plates or fortifications, the firing mechanism also being adapted to function when the deceleration of the missile through the water decreases after the missile has been fired at and missed a target vessel. Furthermore, the device is adapted to be employed against an underwater target such, for example, as a submarine, the hull of a vessel below the water line, or selectively to function instantaneously upon impact of the missile with a target.

The invention relates to a firing device for a fuze employed with an ordnance missile in which the firing mechanism thereof is maintained in a safe position during handling, transportation, or during a firing or launching operation, as the case may be, and in which means are provided for storing electrical energy in the missile as the missileis propelled from a launching rack or a gun, the energy storing means being connected to a normally open inertial switch adapted to remain open during the air flight of the missile toward a target and to close upon impact of the missile therewith and to remain closed until the missile has penetrated the outer plates of the target vessel or the like, whereupon the aforesaid energy storing means is discharged into a second energy storing mean; When penetration of the aforesaid target plates by the missile is completed and the missile decelerates within the interior of the target structure the switch returns to the normal position whereupon the second energy storing means is discharged through an electroresponsive detonator by way of circuit means associated therewith and thus the detonator is fired and the missile exploded. Furthermore, on impact of the missile with the target, the missile is adapted to pierce the outer plates of a target and to be exploded Within the interior thereof by the firing device whereby the force of the explosion is concentrated on the vital structural arrangement in the interior of the target. Thus, the bursting charge within the missile is detonated in time delayed relation with respect to the aforesaid impact of the missile with the target. Hereto fore, such time delay period has been provided by any well known delay element associated with, or arranged within the detonator in a well known manner.

- Patented Aug. 6, 1957 The inertial switch is also constructed and arranged to close and to' remain closed during deceleration of the missile within the water when the missile misses the target, the energy initially stored in the missile being transferred to the second energy storing means as the switch closes and being discharged therefrom through the detonator as the switch returns to the normal position thereof when the deceleration of the missile falls to a predetermined value, thereby to explode the missile.

In accordance with an alternative arrangement of the invention, fuze means selectively operable at will at the time of launching the missile are employed to explode the missile upon complete deceleration thereof as aforementioned, or selectively to explode the missile instantaneouslyupon impact thereof with the target.

One of the objects of the present invention is the provision of a new and improved firing mechanism for an ordnance missile in which the firing means is maintained in a safecondition until the missile is launched from a launching rack, or fired from a gun as the case may be.

Another object of the present invention is to provide a new and improved firing device for an ordnance missile having provision for storing electrical energy therein as the missile is arranged within a launching rack, or the like, as the case may be.

Another object of the present invention is the provision of a new and improved firing device for a fuze in which means are provided for firing an electroresponsive detonator therein when the deceleration of the fuze has reached a predetermined value.

A further object of the invention is to provide a new and improved deceleration discriminating firing mechanism for a rocket fuze having provision for maintaining the rocket in a safe condition during launching and during the free flight of the rocket toward a target vessel, or the like, and adapted to cause explosion of the rocket when the rocket has pierced the plates of a target vessel, or the like, and decelerates within the interior thereof, and having additional provision for selectively rendering the mechanism efiective to explode the rocket instantane ously uponimpact of the rocket with a target.

A further object of the invention is to provide a new and improved acceleration discriminating firing mechanism for an ordnance missile having provision for storing electrical energy therein as the missile is arranged within a launching rack, or the like, as the case may be, and having further provision for transferring the stored energy to an energy storing device upon impact and penetration of the plates of a target vessel or the like, the energy stored in the device being adapted to be discharged through an electroresponsive device thereby to cause detonation thereof in time delayed relation with respect to the aforesaid impact as the missile comes to rest within the interior of the target.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein: Y

' Fig. 1 is a pictorial view showing the manner in which an ordnance missile is functioned by the firing device of the present invention upon deceleration of the missile or instantaneously upon impact with a target vessel;

Fig. 2 is an elevational view of a rocket partially broken away and showing the fuze and the charging arrange ment for the firing mechanism of the present invention; Fig. 3 is an enlarged longitudinal sectional view of the fuze of Fig. 2 and showing the firing device of the present invention arranged therein;

Fig. 4 is a perspective view of the inertial switch employed with the present invention;

Fig. 5 is an enlarged longitudinal sectional view of the device of Fig. 4; I

Fig. 6 is a sectional view taken on line 66 of Fig. 5;

Fig.7 is a circuit diagram of a preferred embodiment of the present invention as applied'to afuze; and;

Fig, 8 is a circuit diagrarnof a modified form. of. the device of Fig. 7.

Referring now tothe. drawings for a. more complete understanding of the inventionand moreparticularly to Fig. 2 thereof, there is shown thereon airocket indicated generally by the reference character 10 comprising a motor tube or casing. 11 having. the usual rocket motor indicated by the numeral 12 arrangedtherein. Secured to one end of the motor tube ll; preferably by-threading the parts together, is an armorpiercing rocket head 13 comprising a shell14 having arranged thereinabursting charge 15. Disposed in one end of the head-13 and attached thereto as by an adapter 16 is the fuze 17 having arranged therein the deceleration discriminating mechanism of the present invention.

The rocket, Fig. 2, is a conventional type finstabilized rocket and the motor thereof comprises the usual component parts such, for example as a propellant18, grid 19 for supporting the propellant within the tube 11, nozzle 21 adapted to direct the gas jet in the desired direction as the propellant burns and to provide for expansion of the gases in the exit cone of the nozzle,

'igniter '22, squib23 arranged in operative relation with respect to the igniter, and conductors 24 attached to the squib and adapted to supply an electrical impulse thereto as the rocket is launched-thereby to fire and ignite the igniter which, in turn, ignites the propellant which propels the rocket towards the target. The usual stabilizing assembly is indicated by the reference 25 and ,is secured to the motor tube 11, Asthe operation and structural arrangement of rockets is well known to those skilled in the art, further detailed description of the operation and structural arrangement thereof is deemed unnecessary as the aforesaid rocket is disclosed for the purpose of more clearly illustrating the manner in which the fuze is armed in response to a predetermined amount of pressure created by the propellant 18 as the propellant burns.

Referring now to Fig. 3, the firing device of the present invention comprises an inertia responsive switch generally indicated by the reference character 26 and'arranged within the fuze casing 17, the switch comprising a pair of members 27-28, Figs. 4 to 6, composed of any insulating material suitable for the purpose such, for example as Bakelite. Secured to the member 28 as by screws or the like 29 and disposed withina recess 31 formed in member'27is an inertial operated reed 32, arranged in normal engagement with a contact member 33 affixed to the member 28.

Threaded within the member 27 is a bushing 34 composed of any material suitable for the purpose such, for example, as steel, or thelike, and having a contact member 35 of brass threaded therein, one end thereof being in predetermined spaced relation with respect to the reed 32. As shown more clearly on Fig. 5,- the. members 27 and 28 are secured together by a pin 36 composed of any insulating material suitable for the purpose such, for example, as Bakelite or any of the synthetic varities thereof, the pin 36 being cemented in a pair of bores 37 formed in members 27 and 28 respectively.

As shown on Fig. 3, a pair of condensers 3839 are arranged within the fuze 17, the condensers being cooperatively associated. and electrically connected to the switch 26 and adapted to function as the switch is actuated in response to deceleration of the missile as will be hereinafter more fully described. It will be understood,

however, that the condenser 38 is charged when the rocket is arranged in the launching rack or tube asthe case may be. 'The charging arrangement for condenser 38 comprises a jack or plug 41, Fig. 2, adapted to be detachably connected to a suitable source of electrical power (not shown) such, for example, as a battery or the like, a pair of conductors 42.43, one end of conductor 42 being secured to one of the prongs of the jack 41, the other end thereof being secured to the charging contact 44, one end of conductor 43 being secured to the other one of the prongs of the jack, the other end thereof being secured to the contact supporting member 45 insulated from contact 44 as at 46, Fig. 3, and supported,

within the tube 11 and grounded thereto by an annular member 47, a conductor member 48 supported within the fuze in engagement with the contact 44 and insulated from the fuze casing as by insulators 49, a conductor 51 connected to member 48 and to condenser 38, and a conductor 70 for'grounding condensers 3839 to the fuze and thus to tube 11. By this arrangement energy is supplied to'the condenser 38 as the rocket is launched, the

' Fig. 3. 'When a sufiicie'ntamount of pressure has entered into chamber 53 in the manner heretofore described the diaphragm 52 actuates the arming switch generally indicated by the numeral 50, as the diaphragm is forced into engagement with the arming plunger 58, as shown on Fig. 3, whereupon the plunger is moved forcibly by the diaphragm suificiently to cause shearing of pin 59 and cause further movement of the plunger to an armed position. When this occurs, the fuze is armed, the arming plunger 58 being in engagement with a pair of arming contacts 61, heretofore in engagement with the collar 62 composed of insulating material and disposed on the arming plunger.

The arming rotor safety means 60 includes the locking ball 63 therefor which moved radially of the plunger upon movement thereof to, armed position, thereby to permit axial movement of the spring loaded locking pin 68 out of opening 69 therefor in the rotor 64, the ball and pin being illustrated in. the released position. The cylindrical arming rotor 64 is also illustrated in the armed position with the primer 65 arranged therein in alignment with electroresponsive detonator 66 andwith the lead-in charge 66' disposed within the fuze and in operativerelation with the booster charge 67. By this arrangement a continuous explosive train is established from the detonator 66 to the booster charge 67, and thus means are provided for firing the bursting charge 15 arranged within the rocket head when the switch 26 is actuated, as will hereinafter be more fully described.

It will be understood, however, that a firing impulse will not be received by the detonator 66, although the fuze is armed, until the forward motion of the rocket has decreased to a predetermined value whereupon the detonator is fired and the rocket exploded when an interval or period of time has elapsed, this delay time being controlled by and suitable adjustment of the inertia switch 26 ashereinafter set forth.

Referring now to the circuit arrangement of Fig. 7, it will be understood, that as the missile is fired from a launching rack or gun, as the case may be, the condenser 38 is charged from a suitable source of electrical power such, for example, as a battery, or the like, by

way of conductors 42-51, the ground connections 70 completing the charging circuit to condenser 38 and thence to conductor 43, the reed 32 of switch 26 being in normal engagement with contact 33 and adapted to remain in engagement therewith during the air flight of the missile toward the target. Upon impact of the missile with the target and in response to the deceleration thereof, the spring reed 32 is moved into engagement with contact 35 and remains in engagement therewith until the missile approaches a state of rest. During the engagement of reed 32 with contact 35, the energy 1n condenser 38 is discharged into condenser 39 by way of conductors 51--71, contact 35, reed 32, conductor 72, condenser 39, and thence by way of the ground connection 70 to the other side of condenser 38. Upon predetermined decrease in the deceleration of the missile and prior to arrestment thereof, the reed 32 returns to its normal position in engagement with contact 33 whereupon the energy in condenser 39 is discharged through the electroresponsive detonator 66 by way of conductor 72, spring element 32, contact 33, conductor 73, detonator 66, a conductor 74, arming contacts 61 in engagement with grounded arming plunger 58, and thence by way of grounded conductor 70 to the other side 'of condenser 39. Thus, the detonator is fired and explosion of the missile occurs in response to a predetermined decrease in the deceleration thereof upon penetration of the target irrespective of the size or type thereof.

Themodified circuit arrangement shown on Fig. 8 comprises the decelerating means for functioning the fuze as heretofore described, and in addition thereto, means are provided for functioning the fuze instantaneously upon impact of the missile with a target vessel or the like, in which a pair of tubes 77, 78 is employed for selecting for operation the means for causing the device to function either instantaneously upon impact of the missile with a target or upon predetermined decrease in the deceleration of the missile. For instantane ous firing, a predetermined voltage such, for example, as from 150 to 180 volts is supplied to the device from a suitable source of electrical energy by way of conductors 42-43 whereupon tubes 77 and 78 are caused to conduct thereby charging condenser 79, condenser 38 also being charged at the same time; It will be understood, however, that when the arming switch 50 is actuated by the aforesaid gas pressure and the plunger is moved into electrical contact with the contact member 61 during the free flight of the rocket toward a target, the fuze is also armed for instantaneous functioning, whereupon the firing device Fig. 8 will function instantaneously upon impact of the missile with the target. Upon impact, the inertial switch 81 is closed in response to the impact and a firing circuit is completed from condenser 79 to the detonator 82. When this occurs the condenser 79 is discharged through the electroresponsive detonator 82 by way of conductor 80 to one terminalof the detonator, the firing circuit to the detonator being completed byway of conductor 90 connected to the other terminal of the detonator and to the inertial switch 81 and thence to ground by way of conductor 74, contacts 61, plunger 58 and conductor 70, thereby causing firing of the detonator and explosion of the missile.

For deceleration functioning of the fuze, a voltage of a predetermined amplitude is supplied to the device, such for example as from 80 to 90 volts, the voltage being of insufficient strength to cause tube 78 to conduct, but of suflicient strength to cause tube 77 to conduct thereby only charging condenser 38.

From the foregoing, it will be understood that with condenser 38 charged, the device of Fig. 8 Will function in the same manner as the device of Fig. 7. Therefore, further detailed description in regards to the deceleration firing arrangement of Fig. 8 is deemed necessary.

Fig. 1 illustrates the manner in which the firing mechanism of the present invention is adapted to function and explode the missile, such, for example, as within a body of water or the interior of a target vessel when thedeceleration of the missile has decreased to a prede termined value, or instantaneously upon impact'of the missile with a target vessel, the target vessel being designated by the letter A.

The dashed line B indicates the flight of a missilethrough the air and water and beyond the target vessel after missing the target vessel. When this occurs the firing device willfunction to fuze and explode the missile; as indicated at point C when the forward motion thereof has decreased to a predetermined value.

The dashed line D indicates the flight of the missile toward the target vessel and a direct hit thereof below the water line of the vessel. When this occurs the firing device will function the fuze and explode the missile when the missile has penetrated the plates of the vessel and the forward motion thereof has decelerated the interior structural arrangement of the vessel as at E. It will be understood, however, that to this end, the switch 26 is adjusted in' any suitable manner by increasing the opening between contacts 33 and 35 as by adjustmentof contact 35 and/or by flexing reed 32 snfl'i ciently to obtain a desired initial pressure against back contact 33, the adjustment in any case being such as to prevent functioning of the firing device upon impact of the missile with the Water.

The dashed line F indicates the air flight of the missile and a direct hit thereof with the super structure of the vessel. When this occurs the instantaneous firing arrange ment of Fig. 8 will function the fuze and explode the missile upon impact thereof with the target vessel at point G, it being understood, however, that in such case, condensers 38 and 79 of the device of Fig. 8 had previously been charged at the time of launching, the circuit arrangement otherwise being adapted to function the fuze in response to the deceleration of the missile, as aforedescribed.

'Briefly stated in summary, the presentinvention com prises the provision of a new and improved deceleration discriminating firing mechanism for an armor piercing rocket, projectile, missile, or the like, in which means are provided for Yflring' the explosive charge arranged within the missile when the deceleration of the missile has decreased to a predetermined value, and in which means are employed for selecting, at the time of launching of the missile, the desired manner of firing of thefuze which may either be instantaneously upon impact of the missile with the target, or when the deceleration of the missile has decreased to a predetermined value, the deceleration firing of the fuze occurring before deceleration of the fuze becomes zero and the instantaneous functioning of the fuze being controlled by an inertial responsive device actuated upon impact of the missile with the target vessel, or the like.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced other than as specifically described.

The invention herein described and "claimed may be manufactured and used by or for the Government of the United States of America for governmental purposes Without payment of any royalties thereon or therefor;

What is claimed as new and desired to be secured by Letters Patent of the United States is:

1. A firing mechanism for a fuze comprising an inertial responsive switch device constructed and arranged to be actuated from an initial position to a moved position in response to an inertial force of a predetermined value, a condenser operatively connected to said inertial device and adapted to be charged with electrical energy from an external source when said inertial device is in said initialposition, a second condenser operatively'connected to said'inertial, device for storing the electrical energy discharged-from said first condenser when the inertial device is in, said moved position, and means operatively connected to said second condenser and to said inertial device and responsive to the energy discharged therethrough from said second condenser when said inertial device has returned to said initial positionin response to a decrease in said inertial force for functioning, the fuze.

2. A firing mechanism for a fuze comprising an inertial responsive switch device constructed andarranged to be actuated from an initial position to a moved position in response to an inertial force of a predeterminedvalue,

means including a normally chargedcondenser operatively,

connected? to said inertial device and adapted to discharge the electrical energy therein when said inertial device is in-ysaid moved position, means including a second condenser operatively connected to said firstcondenser and the inertialswitch for storing theaenergy discharged from the first condenser, and means including a device operatively connected to said second condenser and to said inertial, device and responsive to said energy discharged therethrough from said second condenser when said inertial device has returned to said initial position in response to a decrease in said inertial force for functioning the fuze.

3. A firing mechanism for a fuze comprising an inertial responsive switch device, a resilient element arranged within said inertial device and constructed and arranged to be actuated from an initial position to a moved position in response to an inertial force of a predetermined value, a normally charged condenser operatively connected, to said inertial device and adapted to discharge the electrical energy therein when said element is in said moved position, a second condenser operatively connected to said inertial device for storing said energy discharged fromsaid first condenser, and means including an electroresponsive detonator operatively connected to said inertial device and to said second condenser and fired by the energy discharged therethrough from said second condenser when said element has returned to said initial position in response to a decrease in said inertial force.-

4. A firing mechanism for a fuze comprising an inertial responsive switch device, means including a resilient element arranged within said inertial device and constructed andyarranged to be actuated from an initial position to a movedjposition in response to an inertial force of a predetermined value, a normally charged condenser operatively connected to said inertial device and adapted to discharge the electrical energy therein when said element is in said moved position, a second condenser operatively connected to said inertial device for receiving and storing said energy discharged from said first condenser, and means including an electroresponsive detonator operatively connected to said device and to said second condenser and constructed and arranged to be fired by the energy discharged therefrom when said element has returned to said initial position in response to a decrease in said inertial force.

5. A firing mechanism for a fuze comprising an inertial responsive switch device, a pair of spaced contact members arranged within said inertial device, a resilient element arranged Within said device normally in engagement with one of the contact members and constructed and arranged to be moved into engagement with the other one of said contact members in response to an inertial force of predetermined value, a normally charged condenseroperatively connected to said other one of the contact members and adapted to discharge the electrical energy therein when said element is in engagement with said other one of the contact members, a second condenser operatively connected to said element for receiving the energy discharged from said first condenser, and means includingan,electroresponsive detonator operatively connected tosaid one of the contact membersand saidsecond condenser and constructed and, arranged to be fired in response to the energy discharged from the second condenser when said element has moved into normal engagement with said one of the contact members in response to a decrease in said inertial force.

6. A firing mechanism for a fuze comprising a firing circuit, an inertial responsive switch device, a pair of spaced contact members arranged within said inertial device, a resilient element, disposed within the inertial device normally in engagement with one of the contact members andconstructed and arranged to be moved intoengagement, with the other one of said contact members in response to an inertial force of predetermined value, a charging circuit, a condenser arranged in said charging circuit and connected to said one of the'contact members and adapted to be charged with electrical energy from an external source of electrical power when said element is in engagement with said one of the contact members, a second condenser arranged in said firing circuit and connected to said element for receiving and storing the electrical energy discharged from said first condenser when the element is in engagement with said otherone of the contact members, and an electroresponsive device connected to said second condenser in said firing circuit and arranged to be fired by the energy discharged from said second condenser when the element has rnoved into normal engagement with said one of the contact members in response to a decrease in said inertial force.

7. A firing mechanism for a fuze comprising a normally charged condenser, an inertial responsive switch device, arpair of spaced contact members arranged within said inertial device, a resilient element disposed within the inertial device in normal engagement with one of the contact members and constructed and arranged to be moved into engagement with the other one of said contact members in response to an inertial force of predetermined value, said condenser being connected to said other one of the contact members, a firing circuit, a second condenser arranged in said firing circuit and connected to said element for receiving and storing the electrical energy discharged from said first condenser when the element is in engagement with said other one of the contact members, and an electro-responsive device connected in said firing circuit to said one of the contact members and arranged to be fired by the energy discharged from said second condenser when the element has moved into said normalsengagement with said one of the contact members in response to a decrease in said inertial force.

8. A deceleraration firing device for a rocket comprising, in combination, a casing, a fuze secured within the casing, an inertial switch device arranged within the fuze, a pair of spaced contact members disposed Within said inertial device, an inertial responsive element disposed within said device normally in engagement with one of the contact members and constructed and arranged to be moved into engagement with the other one of the contact members in response to deceleration of the rocket, a condenser disposed within the fuze and operatively connected to said other one of the contact members and adapted to be charged from an external source of electrical power when said element is in engagement with said other one'of the contact members and the rocket is propelled from a launching rack, a second condenser operatively connected to said element for receiving and storing the electrical energy discharged from said first named condenser when the element has been moved into engagement with said other contact member in response to said deceleration of the rocket upon impact thereof with a target, and means responsive to the energy discharged from the second condenser for exploding the rocket when the element is returned into normal engagement with said'one of the contact members in response to a predetermined decrease in the deceleration of the rocket. j

9. A deceleration firing device for a rocket comprising, in combination, a casing, a fuze secured within the casing, an inertial switch devicearranged'within the fuze and having a pair of spaced contact members disposed therein, an inertial responsive element disposed within said device normally in' engagement with one of the contact members and constructed and arranged to be moved into engagement with the other one of the contact members in response to-predetermined deceleration of the rocket, a condenser disposed within the fuze and operatively connected to said other one of the contact members and adapted to be charged from an external source of electrical power when said element is in engagement with said one of the contact members and the rocket is propelled from a launching rack, a second condenser operatively connected to said element for receiving and storing the electrical energy discharged from the first condenser when the element has been moved into engagement with said other contact member in response to said deceleration of the rocket upon impact thereof with a target, an arming switch constructed and arranged to be moved to an armed position during the free flight of the rocket toward said target, and means connected to said arming switch and to the second condenser and responsive to the energy discharged from the second condenser for exploding the rocket when said switch is in the armed position and the element has returned into normal engagement with said one of the contact members in response to a predetermined decrease in the deceleration of the rocket.

10. A deceleration firing device for a rocket comprising, in combination, a casing, an inertial switch device arranged within the casing, a pair of spaced contact members disposed within said inertial device, a resilient inertial responsive element disposed within said device normally in engagement with one of the contact members and constructed and arranged to be moved into engagement with the other one of the contact members in response to predetermined deceleration of the rocket, a condenser disposed within the casing and operatively connected to said other one of the contact members and adapted to be charged from an external source of electrical energy when said element is in engagement with said one of the contact members and the rocket is propelled from the rocket launcher, a second condenser operatively connected to said resilient element for receiving and storing the electrical energy discharged from said first named condenser when the element has been moved into engagement with said other one of the contact members in response to said deceleration of the rocket upon impact thereof with a target or upon movement thereof within said body of water, a contact element arranged within the casing, a spring urged arming plunger releasably supported within the casing and operatively connected to said second condenser and constructed and arranged to be moved into engagement with said contact element when the plunger is released, means including a device or releasing the plunger in response to pressure applied thereto from combustion of the rocket propellant as the rocket travels along a trajectory, means including an electroresponsive detonator operatively connected to said contact element and to said one of the contact members and responsive to the energy discharged from the second condenser when the contact element is in engagement with the plunger and the resilient element has returned into normal engagement with said one of the contact members in response to a predetermined decrease in the deceleration of the rocket, thereby to explode the rocket in time delayed relation with respect to said engagement of the resilient element with said other one of the contact members.

11. A fuze for an ordnance missile comprising, in

combination, first and second energy storage devices, voltage responsivemeans connected to said devices for storing energy in both the devices when electrical energy of predetermined potential is applied to the voltage responsive means or selectively for storing energy in said first device only when electrical energy of a predetermined lesser potential is applied to the voltage responsive means, first and second detonators, an inertia switch device having a pair of spaced contacts and a resilient element normally in'engagement with one of said contacts and constructed and arranged to be moved into engagement with the other one of the contacts in re sponse to predetermined deceleration of the missile, said other one of the contacts being connected to said first energy storage device and said first detonator being connected to said one of the contacts, a third energy storage device connected to said element whereby the energy stored in said first device is transferred and stored in said third device as said element engages the other one of the contacts upon said deceleration of the missile and the energy stored in the third device is discharged through said first detonator as the element engages said one of the contacts upon a predetermined decrease in the deceleration of the missile, and a second inertia responsive switch connected to said second energy storage device and to said second detonator and constructed and arranged to discharge the energy in the second device through said detonator as said second switch closes in response to impact of the missile with a target.

12. A firing mechanism for a fuze comprising a source of potential, an inertial switch movable from an initial position to a moved position in response to an inertial force of a predetermined value and returnable to said initial position upon a decrease of said inertial force, a condenser operatively connected to said source through said inertial switch for storing energy from said source when the inertial switch is actuated to said moved position in response to the application of said inertial force, and means operatively connected to said condenser through said switch upon return thereof to said initial position and responsive to the energy discharged therethrough from the condenser for functioning the fuze.

13. A firing mechanism for a fuze comprising a source of potential, an inertial switch movable from an initial position to an armed position in response to an inertial force of a predetermined value and returnable to said initial position upon decrease in said inertial force, a storage device operatively connected to said source through said inertial switch for storing energy from said source when the switch is actuated to said armed position in response to application of said inertial force, a firing circuit including said switch and storage device and operable to discharge said storage device therethrough upon return of said switch to said initial position, and firing means arranged within said circuit and responsive to the energy discharge therethrough from said storage device for firing said fnze.

14. A fuze for an ordnance missile comprising an inertial switch having a resilient element arranged therein for actuation from an initial position to a moved position in response to an inertal force and returnable to said initial position upon decrease in said inertial force,

pre-charged energy storage means for storing electrical energy when said element is in said initial position, a second energy storage means connected to said precharged storage means through said switch when actuated to said moved position in response to the application of said inertial force for re-storing the energy discharged therethrough from said pre-charged storage means, a firing circuit including the second energy storage means and said switch and operable to provide a discharge path for said second storage means upon return of said switch to said initial position, and firing means arranged within said firing circuit and responsive to the energy discharged through said firing circuit from said second storage means for firingthe'fuze thereby to explode said missile.

15. A fuze for an ordnance missile; comprising; in

for charging said storage device, firing means in said circuit, and contact means operatively connected to said firing means for discharging said stored energy through 10 the, firing meanswhen saidresilient element is moved into engagement'with the contact means in response toa predetermined decrease in the deceleration of the missile thereby to fire said firing means. 1

References-Cited, in the file of this patent r UNITED STATES' PATENTS 1,841,983

2,404,553 Wales July 23, 1946 Ruhlerna'nn Jan. 19, 71932 

